Aeroplane



Fzvaam. UR 1,757,202

y 5, 1930. w. LAMB 1,757,202

AEROPLANE A Filed June 8, 192a v 6 Sheets-Sheet l Izwentar jfa'ua 500a,?-

Z44 AtHUNAU l lbb w. LAMB May 6, 1930.

AEROPLANE Filed June 1928 6 Sheets-Sheet Inventor Ji'as 02205 M Q05 B] M m Ammgy Z44. HIZHUNHU l Ibo W. LAMB AEROPLANE May 6, 1930.

6 Sheets-sheaf Filed June 8, 1928 Inventor Wills 01213 M 244.. AtHUNAU lbb W. LAMB AEROILANE Filed June 8, 1928 6 Sheets-Sheet Inventor ttornqy W. LAMB AEROPLANE May 6, 19309 Filed June 8, 1928 6 Sheets-Sheet Inventor Attorngy Wz/us 17012272 244. AERONAU [US May 6, 1930., w. LAMB 1,757,202

AEROPLANE Filed June 8, 1928 6 Sheets-Sheet- 6 Inventor jizla' Earn/5 M Attorney Z44 AtHUNAUHUb Patentefi May 6, 1930 WIUS LAMB, OF BLAIR, OKLAHOMA AEROPLANE Application filed June 8,

The present invention relates to aeroplanes and has for its prime object to provide an improved control structure therefor.

Another Very important object of the in vention resides in the provision of means for tilting the wings so as to assist the aeroplane in rising from the ground and also to bring the aeroplane out of a nose dive.

A still further very important object of the invention resides in the provision of a control mechanism therefor which is simple in its construction, compact and convenient in its arrangement of parts, strong and durable, thoroughly eflicient and reliable in use 5 and operation, easy to handle, and otherwise well adapted to the purpose for which it is designed.

With the above and numerous other objects in view as will appear as the description proceeds, the invention resides in certain novel features of construction, and in the combination and arrangement of parts as will be hereinafter more fully described and claimed.

In the drawing: Figure 1 is a side elevation of an aeroplane embodying the features of my invention,

Figure 2 is a top plan view thereof, Figure 3 is an enlarged detail vertical longitudinal section through the cockpit of Q the aeroplane,

Figure 4 is a vertical transverse section substantially on the line 4-4 of Figure 3,

Figure 5 is a longitudinal horizontal section taken through the cockpit portion of the fuselage,

Figure 6 is an enlarged detail side elevation of a portion of the control mechanism,

Figure 7 is a sectional view through one of the wings taken substantially on the line 77 of Figure 2,

Figure 8 is a detail plan view of a portion of the control mechanism,

Figure 9 is a detail section through the shaft of one of the Wings looking toward the fuselage,

Figure 10 is a similar section looking in the opposite direction, and

Figure 11 is a vertical sectional view through the wing control levers.

Referring to the drawing in detail it Wlll 1928. Serial No. 283,902.

be seen that the numeral 5 denotes a fuselage mounted on running gear 6 and provided at its tail with a rudder 7 and elevators 8. All these parts may be of conventional construction. In the present embodiment of the invention the cockpit portion of the fuselage 5 is entered through side doors 9 and has a roof 1O thereover which is raised at the cockpit so as to afford side windows 11 and 12 and a front window or shield 13.

By way of example I have shown a monoplane including laterally extending wings W. These wings WV extend laterally from the fuselage and are mounted on the ends of a shaft 15 journaled through the fuselage and through a frame structure 16.

Two seats 17 are mounted on the frame structure one to each side thereof with a space therebetween. A rocker 18 is fixed intermediate its ends to the center of the shaft 15. The forward end of the rocker 18 has attached thereto a cable 19 by means of a clevis 20 or in any other suitable manner. This cable 19 extends down from the clevis and is trained over a pulley 21 journaled in a bracket 22 in the bottom of the cockpit and this cable extends rearwardly and is trained under a pulley 23 at the forward end of a bracket 24 in the bottom of the cock pit. The

able then inclines upwardly and rearwardly and is Wound several times about a drum 25 which is fixed on a shaft 26 journaled in the frame 16 between the seats 17.

The cable then extends downwardly and about a pulley 27 journaled in a bracket 28 in the bottom of the cockpit. From the pulley 27 the cable extends forwardly and is trained under the about a pulley 29 j ournaled in the rear end of the bracket 24 and then extends up and rearwardly to a clevis 3O fixed to the rear end of the rocker 18.

Obviously by rocking the drum 25 the wings W may be tilted in either direction as may be desired. A U-shaped lever 31 has its extremities fixed to the shaft 26 for rotation thereof and as illustrated in Figure 11, the extremities of the lever have spring pressed detents 32 cooperating with notched quadrants 3a and operable through links 35 100 engaged with auxiliary hand levers 36, which are connected together.

It will thus be seen that either the person sitting to the right or the left may control the pitch of the wings by operation of the lever 31 and that the pitch may be maintained at the desired angle of incidence because of the detents and the notched quadrants.

The inverted U-shaped control 37 is pivotally mounted adjacent its extremities by means of pins 38 in brackets 40 rising from the bottom of the frame structure 16. In the upper corners of this control member 37 there are journaled grooved wheels 41 over which is trained a cable 42.

This cable 42 extends across the top of the control member 37 as is clearly shown in Figure 4 and then down around the outer side of the wheels 41, under the wheels 41 and over pulleys 43 journaled in the sides of the control member in and down along the insides of the sides of the control member and over pulleys 45 and then outwardly through notches 46 in the fuselage and 47 in the wings and over pulleys 48 and 49 and then rearwardly under the wings and attached to depending cranks 50 of ailerons 51.

These ailerons 51 have upstanding cranks 52 to which is attached cable 53 which is trained over pulleys 54 and 55 and extends through the wings and through the fuselage. Extending through the sides of the fuselage this cable 52 is passed through slots 57 concentric about the shaft 15 and at the inner ends of the wings through notches 52 Thus it will be seen that by rotating either wheel 41 the ailerons 51 may be tilted up or down in the opposite directions with respect to each other. As is illustrated to advantage in Figure 6 a tie rod 60 is engaged with each extremity of the control member 37. The rod 60 operates crank 61 on shaft 62 journaled through the rear of the cockpit and having cranks 63 fixed intermediate their ends to the extremity thereof and connected with depending cranks 64 and upright cranks 65 of elevators 8 by rods 66 and 67 respectively.

Therefore by moving the control member forwardly and rearwardly the elevators 8 may be tilted as desired. The rudder 7 is controlled by laterally extending cranks 69 with which are connected rods 70 leading to the tail of the fuselage and connected with foot pedals 71.

During ordinary flying the aviator will only use the control 37 and the foot pedals 71 since by the control 37 he may tilt the ailerons and the elevators as desired and with the foot pedals may manipulate the rudder. However, if the aeroplane gets into a nose dive and it is desired to come out of the same quickly the control lever 31 may be manipulated to tilt the wings that is to raise the forward edges thereof which will cause the aeroplane to come out of the nose dive very quickly as will be apparent.

It will also be seen that at the take off if the aviator has no head wind or is limited in his take off space that the forward edges of the wings may be tilted. It will also be noted that the tilting control for the wings may be moved to the position desired and then left alone while the other controls are manipulated.

It is thought that the construction, operation, utility and advantages of this invention will now be quite apparent to those skilled in this art without a more detailed description thereof.

The present embodiment of the invention has been disclosed in detail merely for the purposes of exemplification since in actual practice it attains the features of advantage enumerated as desirable in the statement of the invention and the above description.

It is apparent, however, that the changes in the details of construction, and in the combination and arrangement of parts may be resorted to without departing from the spirit or scope of the invention as hereinafter claimed or sacrificing any of its advantages.

Having thus described my invention, what I claim as new is:

An aeroplane of the class described comprising a fuselage, wings extending laterally from the fuselage, a shaft journaled transversely through the fuselage, said wings being fixed to said shaft and said fuselage having slots concentric about the shaft, ailerons on the wings, connections to the ailerons extending through said slots, and means for rocking the shaft to change the angle of incidence of said wings.

An aeroplane of the class described comprising a fuselage, wings extending laterally from the fuselage, a shaft journaled transyersely through the fuselage, said wings belng fixed to said shaft, a rocker fixed intermediate its ends to the intermediate portion of the shaft within the fuselage, a drum rotatably mounted in the fuselage, a cable having an intermediate portion wound about the drum and means fixing the ends of the cable to the ends of the rocker, and a plurality of pulleys over which the cable is trained so that by rocking the drum the rocker may be rocked for changing the angle of incidence of the wings, notched quadrants, a lever, spring pressed detents on the lever engaging the notched quadrants, and a hand member rockable on the lever and having link connections with the detents so that when the lever is gripped said detents may be released for rocking the drum.

3. An aeroplane of the class described comprisinga fuselage, wings extending laterally from the fuselage, a shaft journaled transversely through thefuselage, said wings being fixed to said shaft, a rocker fixed intermediate its ends to the intermediate portion of the shaft within the fuselage, a drum rotatably mounted in the fuselage, a cable having an intermediate portion wound about the drum and means fixing the ends of the cable to the ends of the rocker, and a plurality of pulleys over which the cables are trained so that by rocking the drum the rocker may be rocked for changing the angle of incidence of the wings, notched quadrants, a lever, spring pressed detents on the lever engaging the notched quadrants, and a hand member rockable on the lever and having link connections with the detents so that when the lever is gripped said detents may be released for rocking the drum, ailerons mounted on the wings, a cable connected with the ailerons for control thereof and extending into the fuselage, and an inverted U-shaped control rockably mounted in the fuselage and having wheels journaled thereon over which the aileron cable is trained.

4. An aeroplane of the class described comprising a fuslage, wings extending laterally from the fuselage, a shaft journaled transversely through the fuselage, said wings being fixed to said shaft, a rocker fixed intermediate its ends to the intermediate portion of the shaft within the fuselage, a drum rotatably mounted in the fuselage, a cable having an intermediate portion wound about the drum and means fixing the ends of the cable to the ends of the rocker, and a plurality of pulleys over which the cables are trained so that by rocking the drum the rocker may be rocked for changing the angle of incidence of the wings, notched quadrants, a lever, spring pressed detents on the lever engaging the notched quadrants, and a hand member rockable on the lever and having link conections with the detents so that when the lever is gripped said detents may be released for rocking the drum, ailerons mounted on the Wings, a cable connected with the ailerons for control thereof and extending into the fuselage, an inverted U-shaped control rockably mounted in the fuselage and having wheels journaled thereon over which the aileron cable is trained, elevators on the tail of the fuselage, and means for controlling the elevators by rocking the inverted U-shaped control.

5. An aeroplane of the class described comprising a fuselage, wings extending laterally from the fuselage, a shaft journaled transversely through the fuselage, said Wings being fixed to said shaft, a rocker fixed intermediate its ends to the intermediate portion of the shaft within the fuselage, a drum rotatably mounted in the fuselage, a cable having an intermediate portion wound about the drum and means fixing the ends of the cable to the ends of the rocker, and a plurality of pulleys over which the cables are trained so that by rocking the drum the rock er may be rocked for changing the angles of incidence of the wings, notched quadrants, a lever, spring pressed detents on the lever engaging the notched quadrants, and a hand member rockable on the lever and having link connections with the detents so that when the lever is gripped said detents may be released for rocking the drum, ailerons mounted on the wings, a cable connected with the ailerons for control thereof and extending into the fuselage, an inverted U-shaped control rockably mounted in the fuselage and having wheels journaled thereon over which the aileron cable is trained, elevators on the tail of the fuselage, and means for controlling the elevators by rocking the inverted U-shaped control, a rudder on the tail of the fuselage,

and foot pedals in the fuselage for controlling the rudder, means operatively connecting the rudders and the foot pedals.

6. An aeroplane comprising a fuselage, wings extending laterally from the fuselage, a shaft journaled transversely in the fuselage, said wings fixed to said shaft, a rocker fixed to the shaft within the fuselage, a drum rotatably mounted in the fuselage, a cable having an intermediate portion wound about the drum and its ends connected to the rocker, a plurality of pulleys over which the cable is trained so that by rocking the drum the rocker is rocked for changing the angle of incidence of the wings, said drum being fixed on the shaft and disposed in the fuselage, a U-shaped lever having its ends fixed to the shaft and its sides straddling the drum, detents on said lever, hand levers on the U- shaped lever and connected together and also connected to the detents, and concave toothed racks below and opposed to said detents and fixed in the fuselage.

In testimony whereof I afiix my signature.

WIUS LAMB. 

